CN107679260A - Precision of being united when on a kind of stationary orbit remote sensing satellite star determines method - Google Patents
Precision of being united when on a kind of stationary orbit remote sensing satellite star determines method Download PDFInfo
- Publication number
- CN107679260A CN107679260A CN201710676809.XA CN201710676809A CN107679260A CN 107679260 A CN107679260 A CN 107679260A CN 201710676809 A CN201710676809 A CN 201710676809A CN 107679260 A CN107679260 A CN 107679260A
- Authority
- CN
- China
- Prior art keywords
- error
- time
- precision
- star
- remote sensing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/12—Timing analysis or timing optimisation
Abstract
Precision of being united when on a kind of stationary orbit remote sensing satellite star determines method, according to time synchronized principle on stationary orbit remote sensing satellite star, the composition and influence factor of time service precision and punctual precision are studied, analyze pulse per second (PPS) trueness error, pps pulse per second signal propagation delay time error, and control computer, attitude measurement equipment (star sensor or gyro), the time correction error of each link such as camera, establish the determination method for precision of being united when on a set of star, solve the problems, such as that prior art can not precisely determine timing tracking accuracy on star, design available for clock synchronization system on stationary orbit remote sensing satellite star, precision analysis, modeling and checking work.
Description
Technical field
Precision of being united during the present invention relates on a kind of stationary orbit remote sensing satellite star determines method, available for stationary orbit remote sensing
Design, precision analysis, modeling and the checking work of clock synchronization system on Satellite.
Background technology
Stationary orbit remote sensing satellite is picture quality when ensuring satellite imagery, it is necessary to camera and the work of attitude measurement equipment
Under unified time reference, base when making satellite imaging data have identical with control measurement data, carried for ground image processing
For the assistance data and view data of high level of synchronization, ensure the high accuracy of satellite image data.
Due to running on geostationary orbit, outside the downward area of coverage in gps satellite, stationary orbit remote sensing satellite profit
Realize that difficulty is big, cost is high with the mode received when gps signal generation pulse per second (PPS) carries out hardware school.Therefore stationary orbit remote sensing is defended
Star typically substitutes gps signal using clock source generation high stable clock signal on star, and becoming the pulse per second (PPS) that swaps out by house keeping computer enters
During row hardware school.
To realize satellite precise time synchronized, accurate whole pps pulse per second signal, the whole pulse per second (PPS) are exported by house keeping computer
Sent once with whole second time information each second, after amplification and branch process of the pps pulse per second signal by time service unit, as tactile
Signal the user that united when being sent to control computer and camera etc. by RS422 EBIs, while pps pulse per second signal institute is right
The whole second time information answered is broadcasted by 1553B buses to user, and the user that united when each is used as complete set using the pps pulse per second signal received
System time service starting point, and time synchronized function on star is completed as time counting signal using internal clocking.Stationary orbit remote sensing is defended
Clock synchronization system forms as shown in Figure 1 on star.
General remote sensing satellite runs on low orbit in the earth, in the effective of gps satellite constellation to obtain high-resolution
The area of coverage, hardware pulse per second (PPS) relatively easily can be produced using gps signal in time synchronized on entering planet, will not depend upon
United when autonomous high precision clock is completed on star function；Stationary orbit communicates and aeronautical satellite provides the user stable communication forwarding
Passage or navigation signal, it is generally fixed to point to, do not possess the in-orbit frequently motor-driven imaging pattern of low-angle, with remote sensing satellite to detecing
The high target location accuracy of observation of eyes target requires different, specifically for the high accuracy of camera and attitude measurement equipment room when system need
Ask.
The content of the invention
Present invention solves the technical problem that it is：A kind of overcome the deficiencies in the prior art, there is provided stationary orbit remote sensing satellite
Precision of being united when on star determines method, and time synchronized essence on stationary orbit remote sensing satellite star can not precisely be determined by solving prior art
The problem of spending, available for the design of clock synchronization system on stationary orbit remote sensing satellite star, precision analysis, modeling and checking work
Make.
The technical scheme is that：Precision of being united when on a kind of stationary orbit remote sensing satellite star determines method, including as follows
Step：
1) pulse per second (PPS) trueness error E is obtained1, pps pulse per second signal propagation delay time error E2, control computer time correction error E3、
Star sensor data markers generates error E4, gyro data markers generation error E5With camera time correction error E6；
2) according to pulse per second (PPS) trueness error E1, pps pulse per second signal propagation delay time error E2, calculate and obtain time service error EA；
3) according to control computer time correction error E3, star sensor data markers generation error E4, gyro data markers generation
Error E5With camera time correction error E6, calculate and obtain time keeping error EB；
4) according to time service error EAWith time keeping error EB, unite precision E when being calculated on stationary orbit remote sensing satellite starTotal
=EA+EB。
Described calculate obtains time service error EASpecific method be：
EA=E1+E2；
Described calculate obtains time keeping error EBSpecific method be：
EB=MAX { E3+MAX[E4, E5], E6}；
Wherein, MAX represents to ask for max function, and MAX { x, y, z } return value is the maximum in x, y, z.
The pulse per second (PPS) trueness error E1By compare house keeping computer export pulse per second (PPS) and its in the whole of bus broadcast
The time difference between moment second obtains.
The pps pulse per second signal propagation delay time error E2Acquisition methods be：House keeping computer pulse per second (PPS) output end and
Oscillograph is sealed in when each between the pulse per second (PPS) input of system user, whole star power-up, measures the transmission of each road pps pulse per second signal respectively
Time delay, continuous statistics a period of time, draw E2Stationary value.
The control computer time correction error E3It is made up of each link error sum inside control computer, including interface core
Processing delay error, crystal oscillator time deviation caused by aging in life cycle are latched when piece delivery lag error, ASIC stars.
The star sensor data markers generates error E4Absolute star when being sent by obtaining star sensor synchronizing signal
When and star sensor data in relative time, then the two addition is obtained；
The gyro data markers generates error E5By the intrinsic time-consuming acquisition for measuring gyro processing data；
The camera time correction error E6Acquisition methods：It is delayed by obtaining plate interior cabling, transmission delay, device saltus step between plate
Along delay parameter, three is added to obtain E6。
The present invention compared with prior art the advantages of be：Precision of being united when on star of the present invention determines method according to stationary orbit
Time synchronized principle on remote sensing satellite star, the composition and influence factor of time service precision and punctual precision are studied, analyze the second
Pulse precision error, pps pulse per second signal propagation delay time error, and control computer, attitude measurement equipment (star sensor or top
Spiral shell), the time correction error of each link such as camera, establish the determination method of precision of being united when on a set of star.Solves stationary orbit remote sensing
Satellite is easily caused timing tracking accuracy on star and is unsatisfactory for ground image processing requirement due to can not utilize gps signal, and traditional
The method of determination can not be directed to precision of being united when the characteristics of such satellite produces hardware pulse per second (PPS) using itself high accuracy real-time clock is carried out
The problem of budget.Precision of being united when described determines that method make use of quiet rail remote sensing satellite work characteristics, realize it is simple, for it is in-orbit when
Checking work of the precision of uniting on ground has good use value.
Brief description of the drawings
Fig. 1 is that clock synchronization system forms on stationary orbit remote sensing satellite star in the inventive method
Fig. 2 is time synchronized flow on stationary orbit remote sensing satellite star in the inventive method
System error decomposing schematic representation when Fig. 3 is on stationary orbit remote sensing satellite star of the present invention
Embodiment
Time synchronized flow is on stationary orbit remote sensing satellite star：House keeping computer is exported using spaceborne high accuracy real-time clock
Sine wave signal, pps pulse per second signal of generation per second, while lock whole moment second corresponding to the pulse per second (PPS), and pass through
The 1553B bus broadcasts whole second time information, the starting point as user job of uniting sometimes；Time service unit selects pps pulse per second signal
As input, amplification, branch and export each road pps pulse per second signal to it is each when system user (camera, attitude measurement equipment), Hou Zhegen
According to the pps pulse per second signal received as timing signal, and counted using respective internal clocking, finally combine letter of whole moment second
Corresponding absolute moment during data sampling is calculated in breath.Idiographic flow is as shown in Figure 2.
Overcome the deficiencies in the prior art of the present invention, there is provided unite precision determination side when on a kind of stationary orbit remote sensing satellite star
Method, according to time synchronized principle on stationary orbit remote sensing satellite star, to time service precision and the composition and influence factor of punctual precision
Studied, analysis pulse per second (PPS) trueness error, pps pulse per second signal propagation delay time error, and control computer, attitude measurement are set
The time correction error of each links such as standby (star sensor or gyro), camera, establish the determination method for precision of being united when on a set of star, modeling
Situation refers to accompanying drawing 3.
The inventive method specifically comprises the following steps：
(1) unite precision E when by stationary orbit remote sensing satellite starTotalIt is divided into time service error EAWith time keeping error EB。
ETotal=EA+EB； (1)
(2) time service link error EABy pulse per second (PPS) itself precision E1With the propagation delay time E of pulse per second (PPS) on the transmission line2Composition.
Time difference on the former hardware pps pulse per second signal and corresponding star between whole moment second, the latter include the time service of time service unit
Propagation delay time of the module to all cables in the time delay value and signal transmission path of pps pulse per second signal.
EA=E1+E2； (2)
E1Obtained by the pulse per second (PPS) and its time difference between whole moment second of bus broadcast that compare house keeping computer output
；E2Acquisition methods：House keeping computer pulse per second (PPS) output end and it is each when unite user (such as control computer, camera) second arteries and veins
Rush between input and seal in oscillograph, whole star power-up, measure the propagation delay time of each road pps pulse per second signal, continuous one section of statistics respectively
Time, draw E2Stationary value.
(3) in time keeping error EBLink：Control computer is in current star hour counter corresponding to the latch of pulse per second (PPS) rising edge
Numerical value, and whole second time information corresponding to pulse per second (PPS) is received by 1553B buses, in nearest controlling cycle according to pulse per second (PPS) school
When effective marker carry out pulse per second (PPS) high accuracy school when；Camera is counted using local clock, and the counter widths meet camera
Do not spill over during whole work, respectively enter counter values now in the rising edge of pulse per second (PPS) and the rising edge of frame synchronization
Row latches, as local imaging moment data.
Control computer time correction error E be present in above-mentioned link3, star sensor data markers generation error E4, gyro data when
Mark generation error E5And camera internal pulse per second (PPS) transmission and processing delay E6。
According to when unite principle, time keeping error EBBy it is each when unite user maximum determine.Therefore：
EB=MAX { E3+MAX[E4, E5], E6}； (3)
Wherein, " MAX " is to ask for max function, and MAX { x, y, z } return value is the maximum in x, y, z.
E3It is made up of each link error sum inside control computer, including interface chip (80F32) delivery lag error,
Processing delay error, crystal oscillator time deviation caused by aging in life cycle are latched during ASIC stars；E4By obtaining star sensitivity
Relative time during absolute star when device synchronizing signal is sent and in star sensor data, then the two addition is obtained；Due to top
Spiral shell is complete passive working method, and control computer sends synchronizing signal to gyro and collects gyro data, E5By measuring top
The intrinsic time-consuming acquisition of spiral shell processing data；E6Acquisition methods：It is delayed by obtaining plate interior cabling, transmission delay, device are jumped between plate
Become along delay parameter (including rising edge, trailing edge), three is added to obtain E6。
(4) according to the pulse per second (PPS) trueness error E acquired1, pps pulse per second signal propagation delay time error E2, control computer
Time correction error E3, star sensor data markers generation error E4, gyro data markers generation error E5With camera time correction error E6,
And then the precision E that united when being calculated according to formula (1) (2) (3) on stationary orbit remote sensing satellite starTotal。
Implement example
This part is by taking certain stationary orbit remote sensing satellite as an example, according to clock source frequency parameter, house keeping computer, time service list
Member, camera, control computer, star sensor, the parameter of gyro and interface configuration, are calculated on star using method proposed by the present invention
When unite precision.System accuracy computation result when table 1 is.
Precision of being united when in the embodiment of table 1 determines result
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (9)
1. precision of being united when on a kind of stationary orbit remote sensing satellite star determines method, it is characterised in that comprises the following steps：
1) pulse per second (PPS) trueness error E is obtained1, pps pulse per second signal propagation delay time error E2, control computer time correction error E3, star it is quick
Sensor data markers generates error E4, gyro data markers generation error E5With camera time correction error E6；
2) according to pulse per second (PPS) trueness error E1, pps pulse per second signal propagation delay time error E2, calculate and obtain time service error EA；
3) according to control computer time correction error E3, star sensor data markers generation error E4, gyro data markers generation error
E5With camera time correction error E6, calculate and obtain time keeping error EB；
4) according to time service error EAWith time keeping error EB, unite precision E when being calculated on stationary orbit remote sensing satellite starTotal=EA+
EB。
2. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 determines method, it is characterised in that：
Described calculate obtains time service error EASpecific method be：
EA=E1+E2。
3. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 determines method, it is characterised in that：
Described calculate obtains time keeping error EBSpecific method be：
EB=MAX { E3+MAX[E4, E5], E6}；
Wherein, MAX represents to ask for max function, and MAX { x, y, z } return value is the maximum in x, y, z.
4. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 or 2 determines method, its feature exists
In：The pulse per second (PPS) trueness error E1By compare house keeping computer export pulse per second (PPS) and its bus broadcast whole moment second
Between the time difference obtain.
5. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 or 2 determines method, its feature exists
In：The pps pulse per second signal propagation delay time error E2Acquisition methods be：House keeping computer pulse per second (PPS) output end and it is each when
Oscillograph is sealed between the pulse per second (PPS) input of system user, whole star powers up, and measures the propagation delay time of each road pps pulse per second signal respectively,
Continuous statistics a period of time, draw E2Stationary value.
6. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 or 3 determines method, its feature exists
In：The control computer time correction error E3It is made up of each link error sum inside control computer, including interface chip passes
Processing delay error, crystal oscillator time deviation caused by aging in life cycle are latched when passing time delay error, ASIC stars.
7. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 or 3 determines method, its feature exists
In：The star sensor data markers generates error E4By obtain star sensor synchronizing signal send when absolute star when and star
Relative time in sensor data, then the two addition is obtained.
8. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 or 3 determines method, its feature exists
In：The gyro data markers generates error E5By the intrinsic time-consuming acquisition for measuring gyro processing data.
9. precision of being united when on a kind of stationary orbit remote sensing satellite star according to claim 1 or 3 determines method, its feature exists
In：The camera time correction error E6Acquisition methods：It is delayed by obtaining plate interior cabling, transmission delay, device hopping edge are prolonged between plate
When parameter, three is added to obtain E6。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710676809.XA CN107679260B (en) | 2017-08-09 | 2017-08-09 | Method for determining satellite time system precision of stationary orbit remote sensing satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710676809.XA CN107679260B (en) | 2017-08-09 | 2017-08-09 | Method for determining satellite time system precision of stationary orbit remote sensing satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107679260A true CN107679260A (en) | 2018-02-09 |
| CN107679260B CN107679260B (en) | 2020-11-20 |
Family
ID=61135542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710676809.XA Active CN107679260B (en) | 2017-08-09 | 2017-08-09 | Method for determining satellite time system precision of stationary orbit remote sensing satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107679260B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731513A (en) * | 2020-06-15 | 2020-10-02 | 航天东方红卫星有限公司 | Method for maintaining regression orbit in high-precision gravitational field based on monopulse orbit control |
| CN111913470A (en) * | 2020-07-20 | 2020-11-10 | 北京控制工程研究所 | Spacecraft control system data validity identification method |
| CN112564842A (en) * | 2020-12-21 | 2021-03-26 | 交控科技股份有限公司 | Time correction method and device for control system of railway vehicle |
| CN114422065A (en) * | 2021-12-16 | 2022-04-29 | 中国空间技术研究院 | High-orbit remote sensing satellite on-satellite time synchronization system and method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2380626A (en) * | 2001-10-04 | 2003-04-09 | Thales Res Ltd | Navigation satellite system |
| CN103592533A (en) * | 2013-10-23 | 2014-02-19 | 航天东方红卫星有限公司 | Data transmission antenna whole-satellite testing method based on minisatellite information system |
| CN103954297A (en) * | 2014-04-08 | 2014-07-30 | 北京空间飞行器总体设计部 | Determination method of optical remote sensing satellite image positioning accuracy |
| CN104730983A (en) * | 2015-03-11 | 2015-06-24 | 航天东方红卫星有限公司 | High-precision time program control method |
| CN105337680A (en) * | 2015-08-07 | 2016-02-17 | 中国人民解放军63892部队 | High-precision network time unifying device and method |
| CN106154822A (en) * | 2015-03-27 | 2016-11-23 | 北京机电工程研究所 | The method for synchronizing time of satellite locking rubidium atomic clock and localizer station |
-
2017
- 2017-08-09 CN CN201710676809.XA patent/CN107679260B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2380626A (en) * | 2001-10-04 | 2003-04-09 | Thales Res Ltd | Navigation satellite system |
| CN103592533A (en) * | 2013-10-23 | 2014-02-19 | 航天东方红卫星有限公司 | Data transmission antenna whole-satellite testing method based on minisatellite information system |
| CN103954297A (en) * | 2014-04-08 | 2014-07-30 | 北京空间飞行器总体设计部 | Determination method of optical remote sensing satellite image positioning accuracy |
| CN104730983A (en) * | 2015-03-11 | 2015-06-24 | 航天东方红卫星有限公司 | High-precision time program control method |
| CN106154822A (en) * | 2015-03-27 | 2016-11-23 | 北京机电工程研究所 | The method for synchronizing time of satellite locking rubidium atomic clock and localizer station |
| CN105337680A (en) * | 2015-08-07 | 2016-02-17 | 中国人民解放军63892部队 | High-precision network time unifying device and method |
Non-Patent Citations (3)
| Title |
|---|
| JIACHAO CHANG ET AL.: ""The research on system error of Inter-Satellite-Link (ISL)measurements for autonomous navigation of Beidou system", 《ADVANCES IN SPACE RESEARCH》 * |
| 田贺祥 等: ""遥感卫星星上时间管理方法"", 《传感器与微系统》 * |
| 翟学明 等: ""基于FPGA的GPS同步授时与守时方案设计与实现"", 《测控技术》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731513A (en) * | 2020-06-15 | 2020-10-02 | 航天东方红卫星有限公司 | Method for maintaining regression orbit in high-precision gravitational field based on monopulse orbit control |
| CN111913470A (en) * | 2020-07-20 | 2020-11-10 | 北京控制工程研究所 | Spacecraft control system data validity identification method |
| CN112564842A (en) * | 2020-12-21 | 2021-03-26 | 交控科技股份有限公司 | Time correction method and device for control system of railway vehicle |
| CN112564842B (en) * | 2020-12-21 | 2022-12-16 | 交控科技股份有限公司 | Control system timing method and device for railway vehicle |
| CN114422065A (en) * | 2021-12-16 | 2022-04-29 | 中国空间技术研究院 | High-orbit remote sensing satellite on-satellite time synchronization system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107679260B (en) | 2020-11-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107679260A (en) | Precision of being united when on a kind of stationary orbit remote sensing satellite star determines method | |
| US7986263B2 (en) | Method and apparatus for a global navigation satellite system receiver coupled to a host computer system | |
| WO2020135382A1 (en) | System, method, and apparatus for synchronizing time service of multiple sensors, and electronic device | |
| CN110856106B (en) | Indoor high-precision three-dimensional positioning method based on UWB and barometer | |
| US20210159995A1 (en) | Systems and methods for timestamp synchronization | |
| CN109525351B (en) | Equipment for realizing time synchronization with time reference station | |
| TWI533011B (en) | Methods and receivers for improving pusle-per-second precision of navigation system time | |
| CN102566408B (en) | Calibration system for satellite clock and calibration method thereof | |
| CN104317354B (en) | The determination method and structure of global clock between a kind of system | |
| CN106093855B (en) | The navigation control method and control system of unmanned plane | |
| CN103744372A (en) | Multisensor time synchronization method for unmanned plane power patrol and system thereof | |
| CN107886531A (en) | A kind of virtual controlling point acquisition methods matched based on laser ranging and object space | |
| CN110554364B (en) | System and method for testing radar signal pulse arrival time measurement accuracy | |
| CN104155664A (en) | Satellite borne receiver timing functional test system and method | |
| CN108318053A (en) | A kind of space optical remote camera imaging moment stated accuracy measurement method and system | |
| KR101868506B1 (en) | MLAT Receiving Unit Using Local Clock and Driving Method of the Same | |
| CN210742507U (en) | Standard time frequency source device based on global navigation satellite system | |
| CN201945685U (en) | High-accuracy time difference of arrival (TDOA) measuring system for distribution type pulse signals | |
| CN113267186B (en) | Data synchronous acquisition system and data synchronous acquisition method | |
| RU2585325C1 (en) | System for synchronising frequency and time scale of remote stations | |
| CN107300688A (en) | A kind of clock frequency Calibration Method in multipoint location system | |
| JP2005134215A (en) | System for measuring difference of signal arrival time | |
| CN107505622A (en) | Multilasered optical radar system and its control method | |
| CN207965976U (en) | A kind of measuring equipment based on laser ranging and object space matching virtual control point | |
| Dyukov et al. | Accuracy of speed measurements using GNSS in challenging environments |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |